Ion Source—Thermal and Thermomechanical Simulation

Victoria V Svotina,Andrey I Mogulkin,Alexandra Y Kupreeva

doi:10.3390/aerospace8070189

Victoria V Svotina, Andrey I Mogulkin + Show 1 more

Open Access

https://doi.org/10.3390/aerospace8070189

Copy DOI

Abstract

The main purpose of this work is to conduct ground development testing of the ion source intended for use the space debris contactless transportation system. In order to substantiate the operating capability of the developed ion source, its thermal and thermomechanical simulation was carried out. The ion source thermal model should verify the ion source operating capability under thermal loading conditions, and demonstrate the conditions for ion source interfacing with the systems of the service spacecraft with the ion source installed as a payload. The mechanical and mathematical simulation for deformation of the ion source ion-extraction system profiled electrodes under thermal loading in conjunction with the prediction of the strained state based on the numerical simulation of the ion source ion-extraction system units, making it possible to ensure the stability of the ion source performance. Good agreement between the thermal and thermo-mechanical ion source simulation results and experimental data has been demonstrated. It is shown that the developed ion source will be functional in outer space and can be used as an element of the space debris contactless transportation system into graveyard orbits.

Highlights

Non-functioning spacecraft (SC), or their fragments are understood to be space debris (SD)
It is shown that the IS developed and manufactured on the basis of the conducted modeling results operates steadily
Its output characteristics correspond to the calculated values with high accuracy, and, the physical and mathematical IS models developed in the course of the project implementation can be extensively used going forward in the development of similar technical devices with a different standard size

Summary

Introduction

Non-functioning spacecraft (SC), or their fragments are understood to be space debris (SD). A large-sized SD can have great residual angular momenta, or can be tumbling, making it difficult to remove it by contact methods, especially in cases with large solar panels and/or uncontrolled high angular velocities. These circumstances increase the risks of destruction for SSC structural elements or SD to be removed, which can lead to an increase in the number of SD fragments with a simultaneous reduction in their size, and, to growing difficulties in their detection and control. Contactless removal methods are of great interest

Objectives

Results

Conclusion